US9429079B2 - Method and apparatus for detecting combustion conditions in combustors of a sequential combustion gas turbine engine - Google Patents

Method and apparatus for detecting combustion conditions in combustors of a sequential combustion gas turbine engine Download PDF

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Publication number
US9429079B2
US9429079B2 US13/647,566 US201213647566A US9429079B2 US 9429079 B2 US9429079 B2 US 9429079B2 US 201213647566 A US201213647566 A US 201213647566A US 9429079 B2 US9429079 B2 US 9429079B2
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United States
Prior art keywords
turbine
gas
species
combustor
gas turbine
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Expired - Fee Related, expires
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US13/647,566
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English (en)
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US20130098054A1 (en
Inventor
Felix Guethe
Dragan Stankovic
Meike Gumprecht-Liebau
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Ansaldo Energia Switzerland AG
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General Electric Technology GmbH
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Assigned to ALSTOM TECHNOLOGY LTD. reassignment ALSTOM TECHNOLOGY LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Gumprecht-Liebau, Meike, GUETHE, FELIX, STANKOVIC, DRAGAN
Publication of US20130098054A1 publication Critical patent/US20130098054A1/en
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Assigned to Ansaldo Energia Switzerland AG reassignment Ansaldo Energia Switzerland AG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GENERAL ELECTRIC TECHNOLOGY GMBH
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/263—Control of fuel supply by means of fuel metering valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N1/00—Regulating fuel supply
    • F23N1/08—Regulating fuel supply conjointly with another medium, e.g. boiler water
    • F23N1/082—Regulating fuel supply conjointly with another medium, e.g. boiler water using electronic means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/003—Systems for controlling combustion using detectors sensitive to combustion gas properties
    • F23N5/006—Systems for controlling combustion using detectors sensitive to combustion gas properties the detector being sensitive to oxygen
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/08—Purpose of the control system to produce clean exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2202/00—Fluegas recirculation
    • F23C2202/50—Control of recirculation rate
    • F23N2021/12—
    • F23N2041/20—
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2221/00—Pretreatment or prehandling
    • F23N2221/12—Recycling exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2241/00—Applications
    • F23N2241/20—Gas turbines
    • Y02E20/328—

Definitions

  • the present invention relates to the technology of gas turbines, to methods for operating a gas turbine, and to gas turbines useful for carrying out said methods.
  • FGR flue gas recirculation
  • ZrO2 sensors could also be used locally to avoid lifetime reduction due to reducing atmospheres and to homogenize flames. Such ZrO2 sensors would be used similar to 3-way catalysts in cars for optimization of operation.
  • One of numerous aspects of the present invention includes a method for operating a gas turbine, which enables improved gas turbine control and performance.
  • Another aspect includes a method for operating a gas turbine, wherein a CO2-containing gas is compressed in a compressor, the compressed gas is used to burn a fuel in at least one subsequent combustion chamber, and the hot combustion gases are used to drive at least one turbine, characterized in that the species concentration of the gas mixture flowing through the gas turbine is measured at several points within the gas turbine by a plurality of species concentration sensors provided in a distributed arrangement, and the measured concentration values are utilized to control the gas turbine and/or optimize the combustion performance of said gas turbine.
  • At least the O2 concentration is measured by said plurality of species concentration sensors.
  • ZrO2 sensors are used as said species concentration sensors.
  • Yet another embodiment is characterized in that the gas turbine is of the sequential-combustion-type with two combustors and two turbines respectively and flue gas recirculation, whereby at least part of the flue gas at the exit of the gas turbine is recirculated and enters the compressor after being mixed with fresh gas, the species concentrations of O2 and preferably other species, especially CO2, CO, NOx and H2O, are measured, and the fuel flow into the second combustor is controlled based on the measured species concentrations.
  • the O2 profile is measured after the first turbine near the place where the first turbine outlet temperature is measured, to identify rich and lean zones in the first combustor.
  • the species measurement is done at atmospheric pressure with fresh air as a reference.
  • the O2 profile is measured inside the first combustor.
  • the measurements are used to extract local values of the flame temperature.
  • Yet another aspect includes a gas turbine which comprises a compressor, a first combustor with a first combustion chamber and first burners, a first turbine downstream of said first combustor, a second combustor with a second combustion chamber and second burners downstream of said first turbine, a second turbine downstream of said second combustor, and means for recirculating part of the flue gas from the exit of the gas turbine to its entrance. It is characterized in that a plurality of species concentration sensors is arranged within the gas flow of the gas turbine, and the species concentration sensors are connected to a control unit, which controls the operation of the gas turbine.
  • fuel supply valves are provided at a fuel supply of the second burners, and said fuel supply valves are operated by said control unit in accordance with the measurements of said species concentration sensors.
  • said species concentration sensors are arranged at distributed circumferential positions with respect to the axis of the gas turbine, and after the first turbine near the place, where the first turbine outlet temperature is measured.
  • said species concentration sensors are arranged at distributed circumferential positions with respect to the axis of the gas turbine, and inside the first combustor.
  • said species concentration sensors are ZrO2 sensors.
  • FIG. 1 shows a longitudinal cross section of a gas turbine with sequential combustion and flue gas recirculation according to an embodiment of the invention
  • FIG. 2 in an axial view, a preferred circumferential distribution of other species concentration sensors of the invention is illustrated.
  • the present disclosure is directed to achieving homogeneity of the gas stream at the exit of the combustor in a gas turbine with sequential combustion and flue gas recirculation.
  • the simplified scheme of such a gas turbine is shown in FIG. 1 :
  • the gas turbine 10 of FIG. 1 includes a rotor 11 with an axis 26 being surrounded by an inner casing 12 .
  • a compressor 13 compresses the incoming working gas.
  • the compressed gas enters a first combustor 14 , 15 with a first combustion chamber 14 and first burners 15 , which receive their fuel at a fuel input 16 .
  • the hot combustion gases of the first combustor 14 , 15 flow through a first turbine 17 and enter a second combustor 18 , 19 with the second combustion chamber 18 and second burners 19 , which receive their fuel and a fuel input 20 .
  • the hot combustion gases of the second combustor 18 , 19 flow through a second turbine 21 to leave the gas turbine 10 as flue gas.
  • Part of the flue gas is recirculated by a recirculating device 27 (dashed line) to the entrance of the compressor 13 to be mixed there with fresh gas or air.
  • the species concentrations of, for example, CO 2 , CO, NOx and especially the 02 content in the combustor exit plane of the first combustor 14 , 15 will probably exhibit some (off design) distribution when measured with fast ZrO2 probes (or any other fast sensor) due to an inhomogeneous distribution of fuel in the first and second combustors 14 , 15 and 18 , 19 , asymmetric cooling air flows, and perhaps an asymmetric O2 pattern at the inflow after mixing recirculated and fresh gas.
  • the fuel flow of the second combustor 18 , 19 shall—according to principles of the present invention—be controlled based on either of the two following measurements:
  • a measurement inside the first combustor 14 , 15 can be more critical since the choice of reference air as well as temperature and pressure is critical. All parameters have an impact on the signal. However, since the goal is to identify spots, where the stoichiometry switches from lean to rich, a very strong change in signal can be expected locally. Therefore even a more problematic and less accurately calibrated signal will exhibit a jump near stoichiometry, which very comfortably enables altering the fuel flow or taking other measures to influence the Lambda profile locally. In principle, this method can also be used to extract local T flame measures as disclosed in the aforementioned document EP 2 107 305.
  • the species concentration sensors 22 or 23 which are of the ZrO2-type used as Lambda sensors for the ICEs (Internal Combustion Engine) of cars, are provided just after the first turbine (sensors 22 ) or within the first combustion chamber 14 (sensors 23 ) in a circumferential distribution, as is shown in FIG. 2 for the plurality of sensors 22 a - 1 . They are connected to a control unit 24 , which controls fuel supply valves 25 at the fuel supply of the second burners 16 (see FIG. 1 ).
  • the use of ZrO2 sensors helps locally to avoid lifetime reduction due to reducing atmospheres and to homogenize flames.
  • species concentration sensor e.g. ZrO2 sensor

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Regulation And Control Of Combustion (AREA)
  • Investigating Or Analysing Materials By Optical Means (AREA)
  • Measuring Oxygen Concentration In Cells (AREA)
US13/647,566 2011-10-14 2012-10-09 Method and apparatus for detecting combustion conditions in combustors of a sequential combustion gas turbine engine Expired - Fee Related US9429079B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH16762011 2011-10-14
CH01676/11 2011-10-14
CH1676/11 2011-10-14

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EP (1) EP2581583B1 (de)
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130232976A1 (en) * 2012-03-08 2013-09-12 General Electric Company Gas turbine fuel flow measurement using inert gas

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CA2801488C (en) * 2010-07-02 2018-11-06 Exxonmobil Upstream Research Company Low emission triple-cycle power generation systems and methods
SG186157A1 (en) * 2010-07-02 2013-01-30 Exxonmobil Upstream Res Co Stoichiometric combustion of enriched air with exhaust gas recirculation
US20140182298A1 (en) * 2012-12-28 2014-07-03 Exxonmobil Upstream Research Company Stoichiometric combustion control for gas turbine system with exhaust gas recirculation
US9587510B2 (en) * 2013-07-30 2017-03-07 General Electric Company System and method for a gas turbine engine sensor
ITMI20131539A1 (it) * 2013-09-18 2015-03-19 Ansaldo Energia Spa Metodo per il controllo di emissioni di un impianto a turbina a gas e impianto a turbina a gas
GB201317175D0 (en) * 2013-09-27 2013-11-06 Rolls Royce Plc An apparatus and a method of controlling the supply of fuel to a combustion chamber
CN103993961A (zh) * 2014-05-08 2014-08-20 清华大学深圳研究生院 涡喷发动机燃料供应系统及涡喷发动机
JP6563312B2 (ja) * 2015-11-05 2019-08-21 川崎重工業株式会社 ガスタービンエンジンの抽気構造
EP3267107B1 (de) * 2016-07-08 2021-03-17 Ansaldo Energia IP UK Limited Verfahren zur steuerung einer gasturbinenanlage

Citations (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5024055A (en) 1988-08-09 1991-06-18 Hitachi, Ltd. Device for detecting combustion conditions in combustors
EP0478481A1 (de) 1990-09-24 1992-04-01 Guy Pavese Verfahren zur Verbesserung, die Verbrennung eines Brenners mit einem Luftgebläse und Einrichtung zur Durchführung dieses Verfahrens
US20040055273A1 (en) * 2002-05-20 2004-03-25 Kabushiki Kaisha Toshiba Gas turbine control system
US20040107701A1 (en) * 2002-05-31 2004-06-10 Yoshiaki Miyake System and method for controlling combustion in gas turbine with annular combustor
EP1531243A2 (de) 2003-11-17 2005-05-18 General Electric Company Verfahren und System zur Integration einen Emissionssensor in einer Gasturbinenregeleinheit
US20060053802A1 (en) * 2004-09-15 2006-03-16 Toshifumi Sasao Ignition detecting method for gas turbine
US20080147295A1 (en) * 2006-12-19 2008-06-19 General Electric Company System and method for operating a compression-ignition engine
CN101309857A (zh) 2005-09-19 2008-11-19 乔治洛德方法研究和开发液化空气有限公司 使用由至少一个燃气轮机产生的含氧气体生产合成气的方法
US7503178B2 (en) 2003-12-23 2009-03-17 Alstom Technology Ltd Thermal power plant with sequential combustion and reduced-CO2 emission, and a method for operating a plant of this type
US7526914B2 (en) * 2005-11-18 2009-05-05 Denso Corporation Heater control device for gas sensor
EP2107305A1 (de) 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Gasturbinensystem und Verfahren
US7694523B2 (en) * 2004-07-19 2010-04-13 Earthrenew, Inc. Control system for gas turbine in material treatment unit
WO2010044958A1 (en) 2008-10-14 2010-04-22 Exxonmobil Upstream Research Company Methods and systems for controlling the products of combustion
US20100115960A1 (en) 2007-06-19 2010-05-13 Alstom Technology Ltd Gas Turbine Installation with Flue Gas Recirculation
EP2287456A1 (de) 2009-08-17 2011-02-23 Alstom Technology Ltd Gasturbine und Verfahren zum Betrieb der Gasturbine
US20130014514A1 (en) * 2011-07-14 2013-01-17 Bryan Wesley Romig Systems and methods for bulk temperature variation reduction of a gas turbine through can-to-can fuel temperature modulation
US8539749B1 (en) * 2012-04-12 2013-09-24 General Electric Company Systems and apparatus relating to reheat combustion turbine engines with exhaust gas recirculation
US20130269362A1 (en) * 2012-04-12 2013-10-17 General Electric Company Methods, systems and apparatus relating to combustion turbine power plants with exhaust gas recirculation
US20140182299A1 (en) * 2012-12-28 2014-07-03 General Electric Company System and method for reheat in gas turbine with exhaust gas recirculation
US20150000296A1 (en) * 2012-03-21 2015-01-01 Alstom Technology Ltd Method for operating a gas turbine and gas turbine for performing the method
US20150345791A1 (en) * 2013-09-27 2015-12-03 Rolls-Royce Plc Apparatus and a method of controlling the supply of fuel to a combustion chamber

Patent Citations (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5024055A (en) 1988-08-09 1991-06-18 Hitachi, Ltd. Device for detecting combustion conditions in combustors
EP0478481A1 (de) 1990-09-24 1992-04-01 Guy Pavese Verfahren zur Verbesserung, die Verbrennung eines Brenners mit einem Luftgebläse und Einrichtung zur Durchführung dieses Verfahrens
US20040055273A1 (en) * 2002-05-20 2004-03-25 Kabushiki Kaisha Toshiba Gas turbine control system
US20040107701A1 (en) * 2002-05-31 2004-06-10 Yoshiaki Miyake System and method for controlling combustion in gas turbine with annular combustor
EP1531243A2 (de) 2003-11-17 2005-05-18 General Electric Company Verfahren und System zur Integration einen Emissionssensor in einer Gasturbinenregeleinheit
US7503178B2 (en) 2003-12-23 2009-03-17 Alstom Technology Ltd Thermal power plant with sequential combustion and reduced-CO2 emission, and a method for operating a plant of this type
US7694523B2 (en) * 2004-07-19 2010-04-13 Earthrenew, Inc. Control system for gas turbine in material treatment unit
US20060053802A1 (en) * 2004-09-15 2006-03-16 Toshifumi Sasao Ignition detecting method for gas turbine
US20090165377A1 (en) 2005-09-19 2009-07-02 L'air Liquide, Societe Anonyme Pour L'etude Et L'exploitation Des Procedes Georges Claude Method for producing synthetic gas using an oxygen-containing gas produced by at least one gas turbine
CN101309857A (zh) 2005-09-19 2008-11-19 乔治洛德方法研究和开发液化空气有限公司 使用由至少一个燃气轮机产生的含氧气体生产合成气的方法
US7526914B2 (en) * 2005-11-18 2009-05-05 Denso Corporation Heater control device for gas sensor
US8103429B2 (en) * 2006-12-19 2012-01-24 General Electric Company System and method for operating a compression-ignition engine
US20080147295A1 (en) * 2006-12-19 2008-06-19 General Electric Company System and method for operating a compression-ignition engine
US20100115960A1 (en) 2007-06-19 2010-05-13 Alstom Technology Ltd Gas Turbine Installation with Flue Gas Recirculation
EP2107305A1 (de) 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Gasturbinensystem und Verfahren
WO2010044958A1 (en) 2008-10-14 2010-04-22 Exxonmobil Upstream Research Company Methods and systems for controlling the products of combustion
EP2287456A1 (de) 2009-08-17 2011-02-23 Alstom Technology Ltd Gasturbine und Verfahren zum Betrieb der Gasturbine
US20130014514A1 (en) * 2011-07-14 2013-01-17 Bryan Wesley Romig Systems and methods for bulk temperature variation reduction of a gas turbine through can-to-can fuel temperature modulation
US20150000296A1 (en) * 2012-03-21 2015-01-01 Alstom Technology Ltd Method for operating a gas turbine and gas turbine for performing the method
US8539749B1 (en) * 2012-04-12 2013-09-24 General Electric Company Systems and apparatus relating to reheat combustion turbine engines with exhaust gas recirculation
US20130269362A1 (en) * 2012-04-12 2013-10-17 General Electric Company Methods, systems and apparatus relating to combustion turbine power plants with exhaust gas recirculation
US20140182299A1 (en) * 2012-12-28 2014-07-03 General Electric Company System and method for reheat in gas turbine with exhaust gas recirculation
US20150345791A1 (en) * 2013-09-27 2015-12-03 Rolls-Royce Plc Apparatus and a method of controlling the supply of fuel to a combustion chamber

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
Office Action issued on Feb. 11, 2015, by the State Intellectual Property Office, P.R. China in corresponding Chinese Patent Application No. 201210461815.0. (8 Pages).
Search Report for Swiss Patent App. No. 1676/2011 (Jan. 20, 2012).

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130232976A1 (en) * 2012-03-08 2013-09-12 General Electric Company Gas turbine fuel flow measurement using inert gas
US9777637B2 (en) * 2012-03-08 2017-10-03 General Electric Company Gas turbine fuel flow measurement using inert gas

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EP2581583A1 (de) 2013-04-17
CN103047009B (zh) 2016-06-22
CN103047009A (zh) 2013-04-17
US20130098054A1 (en) 2013-04-25
EP2581583B1 (de) 2016-11-30

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